Gravity-stabilizer for aeroplanes.



c. E. smz'aa. GRAVITY STABILIZER FOR AEROPLANES.

awmwfoz APPLICATION FILED AUG-l8, 1917- Patented May 14,1918.

2 SHEETSSHEET 1.

C. E. STITZER.

GRAVITY STABILIZER FOR AEROPLANES. APPLICATION FlLED AUG-18, 19H

1 ,266 ,341 I 1 Patented Mayl l, 1918.

2 SHEETS-SHEET 2.

awmmtoz CHARLES E. STITZER, 0F DENVER, COLORADO.

GRAVITY-STABILIZER FOR AEBOPLAN ES.

Application filed August 18, 1917.

To all whom it may concern:

Be it known that I, CHARLES E. STITZER, a citizen of the United States, residing at Denver, in the county of Denver and State of Colorado, have invented certain new and useful Improvements in Gravity-Stabilizers for Aeroplanes, of which the following is a specification.

This invention relates to aeronautics and has more especial reference to an improved stabilizer for aeroplanes.

The invention has for its dominant object to provide a gravity stabilizer capable of being used upon monoplane or biplane machines, whereby the same will be steadied when in flight and will be prevented from overturning or allowing the planes thereof to assume dangerous and undue angles when in flight.

It is a more specific object of the invention to provide a stabilizing means whereby the weight of the engine and the operator are so positioned upon the machine as to be counter-balanced by the traction of the planes, due to their engagement with the air.

Other independent objects are to provide features of construction 'of portions of the stabilizer which tend toward the attainment of the above aims irrespective of the relation in which they are used.

Other objects will be in part obvious and in part pointed out hereinafter.

The invention accordingly consists in the features of construction, combinations of elements and arrangement of parts which will be exemplified in the construction hereinafter set forth, and the scope of the application of which will be indicated in the following claims.

In the accompanying drawings, wherein is shown one of various possible embodiments of my invention 2- Figure l is a side elevation of the stabilizer as applied to a biplane machine;

Fig. 2 is a top plan of the same; and

Fig. 3 is a fragmentary detail partly in section showing the mounting of the operators seatupon the stabilizing means.

Having more particular reference to the drawings and in connection with which like reference characters will refer to corresponding parts throughout the several views, the several planes of the machine are designated by the letters P, these planes, as will be understood, being interconnected through suitable braces b and standards 0, the same Specification of Letters Patent;

Patented May 14, 1918.

Serial No. 188,925.

being arranged against the forward and rear marginal edges thereof. A rudder supporting beam 1 extends rearwardly of the planes and has the usual construction of rudder R pivoted to the rear end thereof.

Upon the forward end of the rudder support 7* a bearing bracket 1 is fixedly mounted and rotata'bly supports the inclined propeller shaft 2 of the machine, the said shaft having a propeller 3 mounted thereon and the outer end of the same provided with a gear 13.

The stabilizing means comprises a bar 5 which extends diagonally upward for a distance slightly above the upper plane P whereat it is connected to a second bar 6, the lower end of which is secured to the forward end of the rudder support 7' as at 7. The lower end of the bar 5 extends below and slightly rearwardly of the lower plane P and is engaged by a bar or beam 7, this beam extending forwardly and upwardly to a point beyond the planes P whereat it is provided with a suitable hull 8. A brace 9 is provided and has its opposite ends engaged with the intermediate portions of the bars 5 and 7, obviously, serving as means for lessening the strain upon the same and equalizing such shock and stress as may be imparted thereto. E designates the elevating plane.

Within the hull 8 which is located upon the forward extremity of the bar 7, an engine bed 10 is supported and receives a suitable engine 11 thereon, which is intergeared to a chain 12 the upper end at of which ongages a gear 13 arranged on the propeller shaft 2. In this way, it will be readily understood, that rotary motion will be imparted to the shaft 2 and its propeller 3.

The operators seat 14 is slidably mounted upon slotted bars 15 supported upon suitable means within the hull 8. Bolts being carried upon the bottom of the said seat and passing through said slots whereupon looking nuts 16 are turned into engagement with the same. In this way, the seat 14 may be secured in adjusted positions upon the bars. From the foregoing, it will be readily un derstood by those skilled in the art that I have provided an eflicient gravity stabilizer for aeroplanes, both of the monoplane and biplane type. Since the weight of the hull, engine and operator are arranged forwardly of and below the planes P, the same will serve as means for stabilizing the planes, preventing swerving of the same or the assuming of dangerous or undue angles there.

by when the machine is in flight. The Weight of the hull, engine and operator, will of course be so arranged upon the forward portion of the bar '7 as to be counter-bah anced by the plane traction caused by the engagement of the same With the air.

Manifestly, the construction shown is capable of considerable modification and such modification as is Within the scope of my claims, I consider Within the spirit of my invention.

I claim 1. A gravity stabilizer for aeroplanes, including a frame having one end connected to the rudder support of the aeroplane and the remaining end arranged below and forward of the planes, said remaining end having the engine and operators seat arranged thereon and positioned so as to have Weight counterbalanced by the plane tract-ion.

2. A gravity stabilizer for aeroplanes, including a frame having one end connected to the rudder support of the aeroplane and the remaining end arranged below and forward of the planes, the said remaining end having the aeroplane hull and engine arranged thereon, an operators seat adjustably supported in said hull, the hull, engine and operators seat being positioned so as to have their combined Weight counter-balanced by the plane traction.

3. A gravity stabilizer for aeroplanes, in-

negates ea? this patent may he obtained tor five cents east, by addressing the 1,2ee,sa1

eluding a frame having one end extending diagonally through and above the planes, a bar engaged with the upper extremity of said frame and the forward end of the rudder support of the aeroplane, the remaining extremity of the frame being arranged below and forwardly of said Planes, bracing means engaged with the intermediate portions of the frame, said remaining end having the engine and operators seat arranged thereon and so positioned as to have their Weight counter-balanced by the plane traction.

4. A gravity stabilizer for aeroplanes, including a substantially V-shaped frame having one extremity extending diagonally through and above said planes, said extremity being connected to the forward end of the rudder support of the aeroplane, the remaining extremity of the frame being arranged below and forward of said planes, the hull and motive means of the aeroplane being arranged upon the forward portion of the remaining extremity, and an operators seat slidable longitudinally of the hull, said hull, motive means and operators seat being so arranged as to have their combined Weight counter-balanced by the plane traction.

In testimony whereof, I afiix my signature hereto.

CHARLES E; STITZER.

Commissioner e52 Entrants.

Waahingten, Z). S. 

